Modelling,simulation, and analysis of HAL Bangalore13; international airport

Air traffic density in India and the world at large is growing fast and posing challenging13; problems. The problems encountered can be parameterized as flight delay, workload of air traffic13; controllers and noise levels in and around aerodromes. Prediction and quantification of these13; parameters aid in developing strategies for efficient air traffic management. In this study, the13; method used for quantifying is by simulation and analysis of the selected aerodrome and air13; space. This paper presents the results of simulation of HAL Bangalore International Airport,13; which is used by civil as well as military aircraft. With the test flying of unscheduled military13; aircraft and the increase in the civil air traffic, this airport is hitting the limit of acceptable delay.13; The workload on air traffic controllers is pushed to high during peak times. The noise contour13; prediction, especially for the test flying military aircraft is sounding a wake up call to the13; communities living in the vicinity of the Airport.13

Simulation And Analysis Of Indian Air Traffic

Air Traffic Density In India And The World At Large Is Growing Fast . The Airspace And Air Traffic Management Therefore Need Augmentation Of System Capability Without Compromising Safety . This Report Addresses The Judicious Use Of Simulation Facilities To Predict Present And Futuristic Problems. It Is Intended To Help Service Providers Plan And Come Out With Strategies For Air Traffic Management. "State Of The Art Simulation Facilities Are Also Useful In Training A Team Of Reliable, Safe And Efficient Air Traffic Controllers . The Report Presents Results Of Simulation Of Three International Airports : One Existing In Bangalore, The One Planned At Devanahalli And The One In Cochin . The Problems Addressed Are Those Of Delay Encountered At The Three Airports, Controller Workload And Noise Contours Around The Bangalore Aerodrome

Modelling, Simulation, and Analysis of HAL BangaloreInternational Airport

Air traffic density in India and the world at large is growing fast and posing challengingproblems. The problems encountered can be parameterized as flight delay, workload of air trafficcontrollers and noise levels in and around aerodromes. Prediction and quantification of theseparameters aid in developing strategies for efficient air traffic management. In this study, themethod used for quantifying is by simulation and analysis of the selected aerodrome and airspace. This paper presents the results of simulation of HAL Bangalore International Airport,which is used by civil as well as military aircraft. With the test flying of unscheduled militaryaircraft and the increase in the civil air traffic, this airport is hitting the limit of acceptable delay.The workload on air traffic controllers is pushed to high during peak times. The noise contourprediction, especially for the test flying military aircraft is sounding a wake up call to thecommunities living in the vicinity of the Airport

Photocatalytic Degradation of p-Cresol by Zinc Oxide under UV Irradiation

Photocatalytic degradation of p-cresol was carried out using ZnO under UV irradiation. The amount of photocatalyst, concentration of p-cresol and pH were studied as variables. The residual concentration and mineralization of p-cresol was monitored using a UV-visible spectrophotometer and total organic carbon (TOC) analyzer, respectively. The intermediates were detected by ultra high pressure liquid chromatography (UPLC). The highest photodegradation of p-cresol was observed at 2.5 g/L of ZnO and 100 ppm of p-cresol. P-cresol photocatalytic degradation was favorable in the pH range of 6–9. The detected intermediates were 4-hydroxy-benzaldehyde and 4-methyl-1,2-benzodiol. TOC studies show that 93% of total organic carbon was removed from solution during irradiation time. Reusability shows no significant reduction in photocatalytic performance in photodegrading p-cresol

Digital Simulation Model for Turboprop Engine

A comprehensive Turboprop Engine model for digital simulation based on the steady state data and transient characteristics has been proposed for a light transport aircraft. The engine and propeller characteristics have been modeled and implemented in Matlab/Simulink environment. The validation has been carried against the flight data and match is found to be satisfactor

Estimation of aircraft fuel consumption for a mission profile neural networks

Todayx2019;s air transportation industry is faced with the challenge of maintaining a viable economic position in the face of unparalleled increase in fuel costs in combination with the ever-present threat of fuel supply shortages. The rapid increase of air traffic makes the problem regarding aviation fuel challenging. The aviation fuel prices comprise an important expenditure for the airliners. Hence, aircraft fuel consumption becomes a relevant issue in the planning and analysis of aviation operations. The key elements that have major effect on fuel consumption are aircraft design and operating methods. Another element that makes a major impact on the aviation fuel consumption is the aircraft delay caused by air traffic congestion. It is necessary to minimize aircraft delays in air and on ground and thereby minimize aviation fuel consumption. This paper presents a method for the fuel consumption estimation, which has fuel efficient trajectory as one of the interesting by-products. The method presented in this paper, uses fuel consumption information directly from the flight manual provided by the aircraft manufacturer to predict fuel consumption accurately using neural network approach. Fuel consumption information is collected from the pilotx2019;s flight manual and segregated with respect to the different phases of flight like climb, cruise and descent. This segregated fuel consumption data is then presented to the neural network for the estimation of fuel consumption for different phases of flight. Fuel consumption is estimated using the neural networks and compared to the actual performance data given in the flight manual for validation. This neural network based information is then used for the estimation of fuel consumption for a chosen mission profile. The concept of fuel efficient trajectory will be used for the studies on optimized aviation fuel consumption which will lead to an improvement of air transport economics

Efficient numerical integration and table lookup techniques for real time flight simulation

A typical flight simulator consists of models of various elements such as the flight dynamic model, filters and actuators, which have fast and slow eigen values in the overall system. This results into an electromechanical control system of stiff ordinary differential equations. Stability, accuracy and speed of computation are the parameters of interest while selecting numerical integration schemes for use in flight simulators. Similarly, accessing huge aerodynamic and engine database in table look-up format at high speed is an essential requirement for high fidelity real time flight simulation. A study was carried out by implementing well known numerical integration and table lookup techniques in a real time flight simulator facility designed and developed in house. Table lookup techniques such as linear search and index computation methodology using novel Virtual Equi-Spacing concept were also studied. It is seen that the multi-rate integration technique and the table look up using Virtual Equi-Spacing concept have the best performance amongst the techniques studied

Studies on optimal aviation fuel consumption-closing report

Air traffic is increasing rapidly in India as well as world. The increase in air traffic causes the increase in consumption of ATF and hence an increase in the cost. The demand for ATF is leading to a shortage of Aviation Turbine Fuel supply and the cost of ATF is escalating. We are already observing that the increase in air traffic is making ATF very expensive. ATF prices become an important expenditure for the airliners. Hence, aircraft fuel consumption becomes a relevant issue for the planning and analysis for aviation operations. Studies on Optimal Aviation Fuel Consumption have been carried out for HAL Bangalore International Airport and Old Hyderabad International Airport. These studies have been carried out using basic concepts of minor rescheduling of flight times for ground operations and allowing aircraft to cruise at fuel optimal altitudes and air operations. Results presented in this report are encouraging as it leads to fuel conservation during ground and air operations. Observations from fuel consumption studies would form an input for Airlines / ATC and AAI to achieve optimal aviation fuel consumption

Nonlinear Modeling of Wind Tunnel Database for a Fighter Aircraft

This report describes the global nonlinear aerodynamic modeling using multivariate orthogonal functions with an application to F-16 data. The multivariate orthogonal13; polynomials are obtained from the independent variable data and then decomposed into ordinary multivariate polynomials. Chebyshev polynomials, which are orthogonal, are used in this case. The final form is a finite multivariate power series expansion for the dependent13; variable in terms of independent variables. MATLAB based software is developed for the nonlinear modeling using multivariate orthogonal polynomials with an application to F-16 data. This report presents the details of13; the software and validation. The wind tunnel F-16 non-dimensional derivatives data is compared against the data obtained using the orthogonal polynomials. The match is found to be satisfactory

Scheduling of control surfaces for aircraft performance optimisation

Two methods for scheduling the leading edge slat and optimizing lift-to-drag ratio (LDR) are compared. One method employs wind tunnel data on pitching moment, lift force, and drag force to obtain the LDR for assumed Mach number, slat position, and AOA while using an elevator setting that is taken as the trim setting for which the pitching moment is zero. The second method uses the complete 6-DOF simulation model and associated trim algorithm to generate the LDR for a given flight condition and aircraft configuration. The comparison shows that the second method is more realistic as well as simple. It is recommended that this technique be used to arrive at control surface schedules for optimal aircraft performance